Online flight testing system and testing method thereof

A flight test and flight control system technology, which is applied in the testing of machines/structural components, measuring devices, aerodynamic tests, etc., can solve the problem of inability to accurately obtain wall shear stress and pressure information, and achieve light weight and small impact , the effect of strong conformal ability

Active Publication Date: 2021-12-17
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the above-mentioned problems existing in the prior art, the present invention provides an online flight test system and its test method, which solves the problem that the wall shear stress and pressure information cannot be accurately obtained under the online flight state of the aircraft

Method used

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  • Online flight testing system and testing method thereof
  • Online flight testing system and testing method thereof
  • Online flight testing system and testing method thereof

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Experimental program
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Effect test

Embodiment 1

[0050] The shear stress test node module is electrically connected to the tester in parallel mode, and the stress test node module is electrically connected to the tester in series mode.

[0051] In the parallel mode, each node is connected to the tester separately, and the tester performs excitation and signal processing; in the series mode, the first node is connected to the tester, and the subsequent nodes are connected to the previous one by one. node.

[0052] The series mode test node includes a flexible substrate, a control unit and a sensing unit. The sensing unit is a piezoresistive, piezoelectric or capacitive pressure sensor. The control unit is used for controlling the signal acquisition of the sensor to be synchronized with the network.

Embodiment 2

[0054] The shear stress test node module is electrically connected to the tester in series mode, and the pressure test node module is electrically connected to the tester in parallel mode.

[0055] In the parallel mode, each node is connected to the tester separately, and the tester performs excitation and signal processing; in the series mode, the first node is connected to the tester, and the subsequent nodes are connected to the previous one by one. node.

[0056] The series mode test node includes a flexible substrate, a control unit and a sensing unit. The sensing unit is a floating, thermal or bottom partition wall shear stress sensor. The control unit is used for controlling the signal acquisition of the sensor to be synchronized with the network.

[0057] In Embodiment 1 and Embodiment 2, a first node fairing and a second node fairing are respectively attached above the shear stress test node module and the pressure test node module.

[0058] See image 3 and Fig...

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Abstract

The invention relates to an online flight testing system and a measurement method thereof, and belongs to the technical field of fluid measurement. The system is characterized in that a flexible wall surface shear stress test node and a flexible pressure test node have strong conformal capability and are installed on an aircraft in an attached mode, so that the installation mode is simple and easy to implement, and the influence on the flow field of the aircraft is small; an airborne fluid wall surface shear stress and pressure synchronous tester is small in size and light in weight, the number of accessible sensors is large, start and stop can be controlled through an aircraft flight control system, and airborne test conditions under the flight state of an aircraft are met; and fairings are attached to the outsides of the nodes and used for buffering sudden change of the surface structure of the joint of the aircraft wall surface and the nodes, so that the measurement result is accurate. According to the fluid wall surface shear stress and pressure online flight testing system and the measurement method thereof, data support is provided for analyzing the flow state of a boundary layer and evaluating the aerodynamic safety of an aircraft.

Description

technical field [0001] The invention belongs to the technical field of fluid measurement, and in particular relates to an online flight test system and a test method for fluid wall shear stress and pressure. Background technique [0002] Fluid wall shear stress refers to the tangential stress generated on the wall due to the action of viscosity when the fluid flows through the surface of the object. It plays an important supporting role in the aerodynamic design and optimization of new fighters and large transport aircraft. [0003] In addition, as the fluid passes over the surface of the aircraft, it generates pressure perpendicular to the surface. Due to the extremely complex airflow environment during flight and the drastic changes in surface pressure, in order to determine the position where the surface of the aircraft has the greatest influence on the state of the surrounding fluid and monitor the flight status of the aircraft, it is very necessary to collect the press...

Claims

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Application Information

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IPC IPC(8): G01M9/06G01L9/08G01L9/12G01L9/06
CPCG01M9/06G01L9/08G01L9/12G01L9/06Y02T90/00
Inventor 罗剑马炳和庞鹏钟思远庄志洪雷航
Owner NORTHWESTERN POLYTECHNICAL UNIV
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